Numerical study of compression corner flowfield using Gao-Yong turbulence model

GAO Ge; ZHANG Chang-xian; YAN Wen-hui; WANG Yong

Numerical study of compression corner flowfield using Gao-Yong turbulence model

GAO Ge^1,2, ,,
ZHANG Chang-xian^1,2,
YAN Wen-hui^1,2,
WANG Yong^1,2

1.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China
2.
Chinese Aeronautical Establishment, Beijing 100012, China

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出版历程
- 收稿日期: 2011-08-16
- 修回日期: 2011-10-31
- 刊出日期: 2012-01-28

Numerical study of compression corner flowfield using Gao-Yong turbulence model

GAO Ge^{1,2
, ,},
ZHANG Chang-xian^1,2,
YAN Wen-hui^1,2,
WANG Yong^1,2

1.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China
2.
Chinese Aeronautical Establishment, Beijing 100012, China

摘要

摘要: A numerical simulation of shock wave turbulent boundary layer interaction induced by a 24° compression corner based on Gao-Yong compressible turbulence model was presented.The convection terms and the diffusion terms were calculated using the second-order AUSM (advection upstream splitting method) scheme and the second-order central difference scheme,respectively.The Runge-Kutta time marching method was employed to solve the governing equations for steady state solutions.Significant flow separation-region which indicates highly non-isotropic turbulence structure has been found in the present work due to intensity interaction under the 24° compression corner.Comparisons between the calculated results and experimental data have been carried out,including surface pressure distribution,boundary-layer static pressure profiles and mean velocity profiles.The numerical results agree well with the experimental values,which indicate Gao-Yong compressible turbulence model is suitable for the prediction of shock wave turbulent boundary layer interaction in two-dimensional compression corner flows.
- shock wave /
- turbulent boundary layer /
- interaction
Abstract: A numerical simulation of shock wave turbulent boundary layer interaction induced by a 24° compression corner based on Gao-Yong compressible turbulence model was presented.The convection terms and the diffusion terms were calculated using the second-order AUSM (advection upstream splitting method) scheme and the second-order central difference scheme,respectively.The Runge-Kutta time marching method was employed to solve the governing equations for steady state solutions.Significant flow separation-region which indicates highly non-isotropic turbulence structure has been found in the present work due to intensity interaction under the 24° compression corner.Comparisons between the calculated results and experimental data have been carried out,including surface pressure distribution,boundary-layer static pressure profiles and mean velocity profiles.The numerical results agree well with the experimental values,which indicate Gao-Yong compressible turbulence model is suitable for the prediction of shock wave turbulent boundary layer interaction in two-dimensional compression corner flows.
- shock wave /
- turbulent boundary layer /
- interaction

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参考文献(15)

[1]	Adnan Q,Nadeem H,Sanjeev S.New scheme for the computation of compressible flows[J].AIAA Journal,2006,44(5):1025-1039.
[2]	Wu M,Martin M P,Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp[J].AIAA Journal,2007,45(4):879-889.
[3]	Edwards J R,Choi J I,Boles J A.Large-eddy/Reynolds-averaged Navier-Stokes simulation of a Mach 5 compression-corner interaction [J].AIAA Journal,2009,46(4):373-385.
[4]	Martin M P,Taylor E M,Wu M,et al.Bandwidth-optimized WENO scheme for the effective direct numerical simulation of compressible turbulence[J].Journal of Computational Physics,2006,220(1):270-289.
[5]	Knight D,Yan H,Panaras A G,et al.Advances in CFD prediction of shock wave turbulent boundary layer interactions[J].Progress in Aerospace Sciences,2003,39(2):2283-2291.
[6]	Bookey P B,Wyckham C,Smits A J,et al.New experimental data of STBLI at DNS/LES accessible Reynolds numbers.AIAA-2005-309,2005.
[7]	Settles G S,Perkins J J,Bogdonoff S M.Investigation of three-dimensional shock/boundary-layer interactions at swept compression corners[J].AIAA Journal,1980,18(7):779-785.
[8]	GAO Ge,YONG Yan.On incompressible turbulent flow: partial average based theory and applications[J].Journal of Hydraulic Research,2005,43(4):399-407.
[9]	LI Zhiqiang,LI Zhengqiang,YAN Wenhui.Numerical simulation of shock wave/flat-plate turbulent boundary layer interaction[J].Journal of Aerospace Power,2008,23(6):1003-1007.(in Chinese)
[10]	YAN Wenhui,YAN Wei,GAO Ge.Simulation of transonic viscous flows around RAE2822 airfoil in Gao-Yong compressible turbulence model[J].Chinese Journal of Computational Physics,2008,25(6):694-700.(in Chinese)
[11]	YAN Wenhui,GAO Ge,YONG Yan.Numerical simulation of 3-D shock wave/turbulent boundary layer interaction using Gao-Yong turbulence model[J].Journal of Aerospace Power,2009,24(10):2193-2200.(in Chinese)
[12]	GAO Ge,YONG Yan.Partial-average-based equations of incompressible turbulent flow[J].International Journal of Non-Linear Mechanics,2004,39(9):1407-1419.
[13]	Settles G S,Vas I E,Bogdonoff S M.Shock wave turbulent boundary layer interaction at high Reynolds number,including separation and flowfield measurements.AIAA-1976-164,1976.
[14]	Kuehn D M.Experimental investigation of the pressure rise required for the incipient separation of turbulent boundary layers in two-dimensional supersonic flow.NASA-Me-1-21-59A,1959.
[15]	Settles G S,Fitzpatrick T J,Bogdonoff S M,Detailed study of attached and separated compression corner flowfields in high Reynolds number supersonic flow[J].AIAA Journal,1978,17(6):579-585.